CA2248966C - Retaining device, especially for the rear igniter of a missile - Google Patents
Retaining device, especially for the rear igniter of a missile Download PDFInfo
- Publication number
- CA2248966C CA2248966C CA002248966A CA2248966A CA2248966C CA 2248966 C CA2248966 C CA 2248966C CA 002248966 A CA002248966 A CA 002248966A CA 2248966 A CA2248966 A CA 2248966A CA 2248966 C CA2248966 C CA 2248966C
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- Prior art keywords
- cap
- trunnion
- rigid
- container
- ejected
- Prior art date
- Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
- Expired - Fee Related
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Classifications
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
- F02K—JET-PROPULSION PLANTS
- F02K9/00—Rocket-engine plants, i.e. plants carrying both fuel and oxidant therefor; Control thereof
- F02K9/95—Rocket-engine plants, i.e. plants carrying both fuel and oxidant therefor; Control thereof characterised by starting or ignition means or arrangements
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F41—WEAPONS
- F41A—FUNCTIONAL FEATURES OR DETAILS COMMON TO BOTH SMALLARMS AND ORDNANCE, e.g. CANNONS; MOUNTINGS FOR SMALLARMS OR ORDNANCE
- F41A17/00—Safety arrangements, e.g. safeties
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F41—WEAPONS
- F41F—APPARATUS FOR LAUNCHING PROJECTILES OR MISSILES FROM BARRELS, e.g. CANNONS; LAUNCHERS FOR ROCKETS OR TORPEDOES; HARPOON GUNS
- F41F3/00—Rocket or torpedo launchers
- F41F3/04—Rocket or torpedo launchers for rockets
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F41—WEAPONS
- F41F—APPARATUS FOR LAUNCHING PROJECTILES OR MISSILES FROM BARRELS, e.g. CANNONS; LAUNCHERS FOR ROCKETS OR TORPEDOES; HARPOON GUNS
- F41F7/00—Launching-apparatus for projecting missiles or projectiles otherwise than from barrels, e.g. using spigots
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- Engineering & Computer Science (AREA)
- General Engineering & Computer Science (AREA)
- Chemical & Material Sciences (AREA)
- Combustion & Propulsion (AREA)
- Mechanical Engineering (AREA)
- Aiming, Guidance, Guns With A Light Source, Armor, Camouflage, And Targets (AREA)
Abstract
A device for retaining an element ejected by a pyrotechnic device when it is fired comprises at least one metal cap placed behind the nozzle of the device and designed to receive the ejected element, the cap being held in position by curved rigid links. The kinetic energy of the captured element carries along the cap and the captured element and the motion of the assembly is braked by the deformation of the rigid links. Application especially to the retaining of the rear igniter of a missile.
Description
RETAINING DEVICE, ESPECIALLY FOR THE REAR IGNITER
OF A MISSILE
BACKGROUND OF THE INVENTION
1. Field of the Invention s The present invention relates to a device for retaining an element ejected by a pyrotechnic device when it is triggered. It can be applied especially to the retaining device of the rear igniter of a missile. More generally, it can be applied to any pyrotechnic device with rear ejection of elements such as the igniter, the explosive bolt, the booster, the skids or the ~o lids.
During the phase of the firing of a pyrotechnic device such as the engine of a missile for example, the igniter of the engine is ejected at high speed backwards and has kinetic energy such that the ejection may cause very great harm to human beings and extensive damage to equipment.
15 2. Description of the Prior Art To obtain protection from the elements that are thrown out, it may be planned to have a system external to the ammunition known as a system "on the launch pad". However, a system of this kind has many drawbacks.
One example, among others, of drawbacks arises especially out of the fact 2o that the launch pad cannot be too close to the rear of the' device. Since they are relatively distant, the elements strike the launch pad with a kinetic energy that is all the greater. Consequently, the launch pad needs to have a sufficiently great mass for more material is needed to absorb the energy.
This fact then leads to great complexity in the control servo-mechanisms of 25 the launch pad. Furthermore, the relative distance of the launch pad does not always ensure that the elements thrown out will be captured in a reliable way.
Another approach may for example consist in eliminating the ejection. To prevent rear ejection from a pyrotechnic device, it is possible to 3o ignite its engine from the front. In this case, the pyrotechnic elements are integrated during the assembling of the missile, entailing the risks associated with the handling and the in-plant testing of primed explosive elements.
The positioning of the igniter in the rear of the engine during the final phase of integration minimizes the pyrotechnical risks, especially risks in 35 the plant, but leads to the ejection of the igniter at the firing stage. In addition to the flame effects, the structures located in the rear of the firing line receive, as mentioned here above, the projectiles that are constituted by the ejected elements. Given their high speed, which is greater than 100 m/s, these elements may possess kinetic energy of several hundreds of Joules.
These projectiles may therefore cause major damage to neighboring structures or even cause injuries to operators, even if they are shielded, especially owing to the risks of ricochets that are impossible to control.
To prevent the risks associated with pyrotechnic devices of this kind during the firing stage while at the same time keeping the advantages i o associated with rear firing without using the launch pad to receive the ejected elements, it is necessary to capture these elements by means of a retaining device fixedly joined to the container of the device. In the case of application to a missile for example, the capturing device must in particular correspond to the following requirements:
15 ~ the pyrotechnic elements should be captured and held captive during the phase of departure of the missile, namely for a time interval of about 0.2 seconds;
~ the nozzle and the rear of the missile should be released from the missile at high speed, for example within less than 5 ms, to a distance of 2o about 100 mm, but the movement should remain compatible with the templates chosen;
~ the capturing device should not cause deterioration or disturbances that might lead to a defective launch, and furthermore the retaining forces should be compatible with the capacities of compensation of 25 the servo-mechanisms of the missile-launching turret;
~ the capturing device should be capable of withstanding the environmental stresses of the ammunition, namely those of the missile and container.
SUMMARY OF THE INVENTION
ao The aim of the invention is to enable the making of a device that corresponds especially to the above requirements. To this end, an object of the invention is a device for retaining an element ejected by a pyrotechnic device wherein said device comprises at least one metal cap placed behind a5 cap being held in position by curved rigid links, the kinetic energy of the ejected element carrying along the cap and the captured element, the motion of the assembly being braked by the deformation of the rigid links.
The main advantages of the invention are the following: it can be used to obtain a device in the form of a kit that is set so that it is ready to be used, the device can be mounted on a missile during the final integration of the pyrotechnic elements, it ca.n work under very harsh conditions and has very great operating safety, it can be mounted on a missile or any other pyrotechnic device that is already made but has not been fitted out with a retaining system and the making and assembly of the device are i o economical.
BRIEF DESCRIPTION OF THE DRAWINGS
Other features and advantages of the invention shall appear from the following description made with reference to the appended drawings, of which:
- Figure 1 shows a possible exemplary embodiment of a device according to the invention;
- Figure 2 shows the above exemplary embodiment in a view along AA of Figure 1 associated with the elements of a pyrotechnic device;
- Figure 3 shows a device according to the invention in a deployed position;
- Figure 4 shows a possible exemplary embodiment of a cap used in a device according to the invention;
- Figure 5 shows the above exemplary embodiment in a view along BB of Figure .
MORE DETAILED DESCRIPTION
Figures 1 and 2 show a possible exemplary embodiment of a device according to the invention to retain the igniter 1 of a pyrotechnic device 3, for example a missile, during the firing phase. The igniter actually has, firstly, a part 101 that melts during its operational phase. This part is so the pyrotechnic charge of the igniter. The igniter has, secondly, a solid part comprising essentially its connector 102 through which it is connected by a cable (not shown) to the general connector of the missile. It is through this cable and this connector 102 that the firing command is transmitted. The part of the igniter that is ejected is actually the part of the igniter that remains solid since its pyrotechnic charge 101 is consumed for the firing. The igniter 1 is generally ejected with a speed of over 100 m/s and hence with very great energy. Hereinafter, the pyrotechnic device considered is, for example, the engine of a missile.
A device according to the invention comprises a metal cap 6 placed behind the outlet of the nozzle 2 of the missile 3. The cross-section of the missile and the cap are substantially concentric. The cap 6 is designed especially to receive the igniter 1 during its ejection backwards. A
shock-absorbing buffer 12 is used for example as a strap between the cap 6 and the rear hood 5 of the missile container 4. The cap is held in position by ~o means of curved rigid links 7, which for example are made of metal. These curved links have for example the shape of serpentine coils. They are for example three in number. Hereinafter, reference shall be made to serpentine coils but any other shape of curved lines is possible. The serpentine coils are made of a material which in particular withstands great ~ 5 heat due especially to the flame effect. A serpentine coil 7 is connected to the container 4 by a support 8. The fastening of a support to the container is done for example by screws 81. The impervious sealing of this fastening is obtained by bonding identical to the other tight-sealing fixtures of the container.
2o When the missile 3 is launched, the arrival of the igniter 1 in the cap 6 causes the rear hood 5 to break and releases the deployment of the retaining device according to the invention. The kinetic energy of the igniter 1 and the pressure of the gases coming from the nozzle 2 carry along the cap 6 and the igniter 1 captured by this cap 6.. The motion of the assembly 25 is hampered by the deformation of the serpentine coils 7 which stretch during this motion. The curved shape of the serpentine coil means that it can work only under traction during deployment, thus preventing rupture under bending forces. The material of the serpentine coil however has low rupture strength so as to obtain the greatest possible stretching. To this end, the so serpentine coils are made for example of soft steel.
Each serpentine coil 7 works together with the cap 6 and with its support 8 on the container by hinges which minimize the risks of parasitic bending forces, hence the risks of breakage through these bending forces.
To this end, a serpentine coil is articulated by trunnions 9, 10 at its support 8 35 and the cap 6. Consequently, during the deployment of the serpentine coils 7, they are hinged in a rotational motion with respect to the cap and the support without any risk of breaking under bending forces, since the rotational motions enable them to extend substantially in parallel to the thrust caused by the ejection of the igniter and by the gases. The hinging trunnions 5 9, 10 are for example tapped perpendicularly to their axis of rotation, the ends of the serpentine coils being then screwed into these holes. For a serpentine coil 7, the trunnion 9 of the first hinge oscillates in the support fixed to the container and the trunnion 10 of the second hinge oscillates in a nut 11 wedged into the cap 6 on the side of the cap opposite the igniter 1.
~ o These oscillations are done along an axis that is substantially perpendicular to the tangent to the rigid link 7 at the meeting point of this link with the trunnions.
Figure 3 shows a device according to the invention as described with reference to Figures 1 and 2 in a deployed position, once the firing is i s over. The igniter 1 has been captured by the cap 6. The serpentine coils, of which two out of three have been shown, are in their elongated position. The igniter is retained by the cap 6 and the serpentine coils 7 which are themselves fixedly joined to the container 4 by means of their hinge on the supports 8.
2o Figure 2 shows that the connector 102 of the ignites is for example fitted out with a bell 13 designed to cushion the shock of arrival of the ignites 1 on the cap 6. To increase the cushioning effect, the bell is for example split. The bell 13 furthermore helps to guide and keep the ignites 1 in the cap and thus to prevent rebounds. The transmission cable for the igniting 25 command (not shown) connecting the connector of the ignites to the general connector of the missile passes for example through the cap to further facilitate the guidance of the connector 102 of the ignites in the cap 6.
Figures 4 and 5 show an exemplary embodiment of the cap 6.
Figure 5 is a sectional view along BB of Figure 4. This Figure 4 is a view so along F of Figure 5. The shape of the cap makes it possible in particular to facilitate capture and the holding of the ignites during the deployment phase.
Its shape furthermore has aerodynamic properties designed to minimize drag stresses. Furthermore, while it is nevertheless simpler to make a solid part, a cap shape, namely a hollow shape 60 generated by revolution, with its s5 aperture opposite the ignites 1, has been adopted so as to optimize the s weight of the cap. For the weight of the cap should not be so great that it gets released rapidly.
The cap has a shape with a symmetry of revolution and furthermore has an internal funnel shape 64 to receive the igniter 1. The section 61 of the cap has a rounded summit 62 facing the igniter 1. A
cylindrical part 68 extends beyond its base 63 opposite its summit 62 in the form of an end of the funnel 64. This in particular makes the holding of the igniter 1 in the cap 6 more reliable. The sections 65 of the cap 6, which go from the base 63 to the summit 62, are for example rectilinear.
~ o The cap 6 has apertures 66 to enable the passage of the serpentine coils 7 and, more particularly, the passage of the ends of the serpentine coils fastened to the trunnions 10 of the hinges. A ring 67 which surrounds for example the above-mentioned cylindrical part 68 of the cap is used in particular to block the nuts 11 which work together with the trunnions i 5 10. The ring 67 has recessed portions 69 to let through the nuts 11 which are thereafter blocked between the inner face of the cap and the wide parts of the ring 67. The mounting of a nut 11 and then of a serpentine coil 7 can then for example be done by placing the nut between the ring 67 and the inner face of the cap, in making its tapped hole face the aperture 66 of the 2o cap and then screwing the end of the serpentine coil 7 into this tapped hole through the aperture 66. Furthermore, the nut 11 provides for the efficient tight-sealing of the hinges. This makes it possible in particular to prevent a so-called chimney effect, namely the passage of the flame during the firing.
This therefore prevents local melting and enables retention in the flame of 25 the engine for a duration of over 200 ms. The thickness of the section 61 of the cap makes it possible both to minimize its weight so that it is swiftly released as indicated here above and to give it mechanical and thermal strength. To this end, the cap which is made of steel has a thickness, for example, of about 1 millimeter. The cap is made, for example, of stainless 3o steel with high mechanical characteristics.
The device according to the invention can be used under severe conditions. In particular, with regard for example to mechanical shocks of docking with and of the departure of other missiles, or with regard to vibrations in transportation, mechanical strength is obtained by maintaining 35 the cap 6 by means of serpentine coils 7. The serpentine coils are, to this end, slightly tensioned and they abut the supports 8 fixed to the container 4.
The shock-absorbing buffer 12 complements the holding action while at the same time damping the vibrations. The choice of the materials of the components of a device according to the invention furthermore enables it to withstand corrosive gases or heat shock.
A device according to the invention furthermore has great security of operation, especially through the tight sealing of certain parts, for example at the hinges as described here above, through the fact that it is rapidly released from the outlet of the nozzle as well as its great geometrical ~o deformation which moves the retained element to a relatively great distance away from the nozzle.
A device according to the invention can be delivered in the form of a kit so that it is installed especially on missiles already integrated into operational containers or batteries. More generally, it may be mounted on any missile or any pyrotechnic device already made but not provided with a retaining system. A kit comprises for example a set formed of serpentine coils 7 hinged around the cap 6 and the supports 8. These supports 8 are designed for example to be fixed to the container of a missile. The kit furthermore comprises for example a shock-absorbing buffer 12 and a bell 20 13. Since the kit is set in the plant, its installation may be done by drilling the tube of the container in particular to affix the supports 8 of the serpentine coils and then by bonding the rear hood and the sealing fixtures. An operation of this kind requires only a few minutes. It is therefore not costly.
The device according to the invention has been described by way 25 of an example for the retaining of an igniter. However, it can be applied to other elements ejected by pyrotechnic devices such as for example explosive bolts or boosters.
OF A MISSILE
BACKGROUND OF THE INVENTION
1. Field of the Invention s The present invention relates to a device for retaining an element ejected by a pyrotechnic device when it is triggered. It can be applied especially to the retaining device of the rear igniter of a missile. More generally, it can be applied to any pyrotechnic device with rear ejection of elements such as the igniter, the explosive bolt, the booster, the skids or the ~o lids.
During the phase of the firing of a pyrotechnic device such as the engine of a missile for example, the igniter of the engine is ejected at high speed backwards and has kinetic energy such that the ejection may cause very great harm to human beings and extensive damage to equipment.
15 2. Description of the Prior Art To obtain protection from the elements that are thrown out, it may be planned to have a system external to the ammunition known as a system "on the launch pad". However, a system of this kind has many drawbacks.
One example, among others, of drawbacks arises especially out of the fact 2o that the launch pad cannot be too close to the rear of the' device. Since they are relatively distant, the elements strike the launch pad with a kinetic energy that is all the greater. Consequently, the launch pad needs to have a sufficiently great mass for more material is needed to absorb the energy.
This fact then leads to great complexity in the control servo-mechanisms of 25 the launch pad. Furthermore, the relative distance of the launch pad does not always ensure that the elements thrown out will be captured in a reliable way.
Another approach may for example consist in eliminating the ejection. To prevent rear ejection from a pyrotechnic device, it is possible to 3o ignite its engine from the front. In this case, the pyrotechnic elements are integrated during the assembling of the missile, entailing the risks associated with the handling and the in-plant testing of primed explosive elements.
The positioning of the igniter in the rear of the engine during the final phase of integration minimizes the pyrotechnical risks, especially risks in 35 the plant, but leads to the ejection of the igniter at the firing stage. In addition to the flame effects, the structures located in the rear of the firing line receive, as mentioned here above, the projectiles that are constituted by the ejected elements. Given their high speed, which is greater than 100 m/s, these elements may possess kinetic energy of several hundreds of Joules.
These projectiles may therefore cause major damage to neighboring structures or even cause injuries to operators, even if they are shielded, especially owing to the risks of ricochets that are impossible to control.
To prevent the risks associated with pyrotechnic devices of this kind during the firing stage while at the same time keeping the advantages i o associated with rear firing without using the launch pad to receive the ejected elements, it is necessary to capture these elements by means of a retaining device fixedly joined to the container of the device. In the case of application to a missile for example, the capturing device must in particular correspond to the following requirements:
15 ~ the pyrotechnic elements should be captured and held captive during the phase of departure of the missile, namely for a time interval of about 0.2 seconds;
~ the nozzle and the rear of the missile should be released from the missile at high speed, for example within less than 5 ms, to a distance of 2o about 100 mm, but the movement should remain compatible with the templates chosen;
~ the capturing device should not cause deterioration or disturbances that might lead to a defective launch, and furthermore the retaining forces should be compatible with the capacities of compensation of 25 the servo-mechanisms of the missile-launching turret;
~ the capturing device should be capable of withstanding the environmental stresses of the ammunition, namely those of the missile and container.
SUMMARY OF THE INVENTION
ao The aim of the invention is to enable the making of a device that corresponds especially to the above requirements. To this end, an object of the invention is a device for retaining an element ejected by a pyrotechnic device wherein said device comprises at least one metal cap placed behind a5 cap being held in position by curved rigid links, the kinetic energy of the ejected element carrying along the cap and the captured element, the motion of the assembly being braked by the deformation of the rigid links.
The main advantages of the invention are the following: it can be used to obtain a device in the form of a kit that is set so that it is ready to be used, the device can be mounted on a missile during the final integration of the pyrotechnic elements, it ca.n work under very harsh conditions and has very great operating safety, it can be mounted on a missile or any other pyrotechnic device that is already made but has not been fitted out with a retaining system and the making and assembly of the device are i o economical.
BRIEF DESCRIPTION OF THE DRAWINGS
Other features and advantages of the invention shall appear from the following description made with reference to the appended drawings, of which:
- Figure 1 shows a possible exemplary embodiment of a device according to the invention;
- Figure 2 shows the above exemplary embodiment in a view along AA of Figure 1 associated with the elements of a pyrotechnic device;
- Figure 3 shows a device according to the invention in a deployed position;
- Figure 4 shows a possible exemplary embodiment of a cap used in a device according to the invention;
- Figure 5 shows the above exemplary embodiment in a view along BB of Figure .
MORE DETAILED DESCRIPTION
Figures 1 and 2 show a possible exemplary embodiment of a device according to the invention to retain the igniter 1 of a pyrotechnic device 3, for example a missile, during the firing phase. The igniter actually has, firstly, a part 101 that melts during its operational phase. This part is so the pyrotechnic charge of the igniter. The igniter has, secondly, a solid part comprising essentially its connector 102 through which it is connected by a cable (not shown) to the general connector of the missile. It is through this cable and this connector 102 that the firing command is transmitted. The part of the igniter that is ejected is actually the part of the igniter that remains solid since its pyrotechnic charge 101 is consumed for the firing. The igniter 1 is generally ejected with a speed of over 100 m/s and hence with very great energy. Hereinafter, the pyrotechnic device considered is, for example, the engine of a missile.
A device according to the invention comprises a metal cap 6 placed behind the outlet of the nozzle 2 of the missile 3. The cross-section of the missile and the cap are substantially concentric. The cap 6 is designed especially to receive the igniter 1 during its ejection backwards. A
shock-absorbing buffer 12 is used for example as a strap between the cap 6 and the rear hood 5 of the missile container 4. The cap is held in position by ~o means of curved rigid links 7, which for example are made of metal. These curved links have for example the shape of serpentine coils. They are for example three in number. Hereinafter, reference shall be made to serpentine coils but any other shape of curved lines is possible. The serpentine coils are made of a material which in particular withstands great ~ 5 heat due especially to the flame effect. A serpentine coil 7 is connected to the container 4 by a support 8. The fastening of a support to the container is done for example by screws 81. The impervious sealing of this fastening is obtained by bonding identical to the other tight-sealing fixtures of the container.
2o When the missile 3 is launched, the arrival of the igniter 1 in the cap 6 causes the rear hood 5 to break and releases the deployment of the retaining device according to the invention. The kinetic energy of the igniter 1 and the pressure of the gases coming from the nozzle 2 carry along the cap 6 and the igniter 1 captured by this cap 6.. The motion of the assembly 25 is hampered by the deformation of the serpentine coils 7 which stretch during this motion. The curved shape of the serpentine coil means that it can work only under traction during deployment, thus preventing rupture under bending forces. The material of the serpentine coil however has low rupture strength so as to obtain the greatest possible stretching. To this end, the so serpentine coils are made for example of soft steel.
Each serpentine coil 7 works together with the cap 6 and with its support 8 on the container by hinges which minimize the risks of parasitic bending forces, hence the risks of breakage through these bending forces.
To this end, a serpentine coil is articulated by trunnions 9, 10 at its support 8 35 and the cap 6. Consequently, during the deployment of the serpentine coils 7, they are hinged in a rotational motion with respect to the cap and the support without any risk of breaking under bending forces, since the rotational motions enable them to extend substantially in parallel to the thrust caused by the ejection of the igniter and by the gases. The hinging trunnions 5 9, 10 are for example tapped perpendicularly to their axis of rotation, the ends of the serpentine coils being then screwed into these holes. For a serpentine coil 7, the trunnion 9 of the first hinge oscillates in the support fixed to the container and the trunnion 10 of the second hinge oscillates in a nut 11 wedged into the cap 6 on the side of the cap opposite the igniter 1.
~ o These oscillations are done along an axis that is substantially perpendicular to the tangent to the rigid link 7 at the meeting point of this link with the trunnions.
Figure 3 shows a device according to the invention as described with reference to Figures 1 and 2 in a deployed position, once the firing is i s over. The igniter 1 has been captured by the cap 6. The serpentine coils, of which two out of three have been shown, are in their elongated position. The igniter is retained by the cap 6 and the serpentine coils 7 which are themselves fixedly joined to the container 4 by means of their hinge on the supports 8.
2o Figure 2 shows that the connector 102 of the ignites is for example fitted out with a bell 13 designed to cushion the shock of arrival of the ignites 1 on the cap 6. To increase the cushioning effect, the bell is for example split. The bell 13 furthermore helps to guide and keep the ignites 1 in the cap and thus to prevent rebounds. The transmission cable for the igniting 25 command (not shown) connecting the connector of the ignites to the general connector of the missile passes for example through the cap to further facilitate the guidance of the connector 102 of the ignites in the cap 6.
Figures 4 and 5 show an exemplary embodiment of the cap 6.
Figure 5 is a sectional view along BB of Figure 4. This Figure 4 is a view so along F of Figure 5. The shape of the cap makes it possible in particular to facilitate capture and the holding of the ignites during the deployment phase.
Its shape furthermore has aerodynamic properties designed to minimize drag stresses. Furthermore, while it is nevertheless simpler to make a solid part, a cap shape, namely a hollow shape 60 generated by revolution, with its s5 aperture opposite the ignites 1, has been adopted so as to optimize the s weight of the cap. For the weight of the cap should not be so great that it gets released rapidly.
The cap has a shape with a symmetry of revolution and furthermore has an internal funnel shape 64 to receive the igniter 1. The section 61 of the cap has a rounded summit 62 facing the igniter 1. A
cylindrical part 68 extends beyond its base 63 opposite its summit 62 in the form of an end of the funnel 64. This in particular makes the holding of the igniter 1 in the cap 6 more reliable. The sections 65 of the cap 6, which go from the base 63 to the summit 62, are for example rectilinear.
~ o The cap 6 has apertures 66 to enable the passage of the serpentine coils 7 and, more particularly, the passage of the ends of the serpentine coils fastened to the trunnions 10 of the hinges. A ring 67 which surrounds for example the above-mentioned cylindrical part 68 of the cap is used in particular to block the nuts 11 which work together with the trunnions i 5 10. The ring 67 has recessed portions 69 to let through the nuts 11 which are thereafter blocked between the inner face of the cap and the wide parts of the ring 67. The mounting of a nut 11 and then of a serpentine coil 7 can then for example be done by placing the nut between the ring 67 and the inner face of the cap, in making its tapped hole face the aperture 66 of the 2o cap and then screwing the end of the serpentine coil 7 into this tapped hole through the aperture 66. Furthermore, the nut 11 provides for the efficient tight-sealing of the hinges. This makes it possible in particular to prevent a so-called chimney effect, namely the passage of the flame during the firing.
This therefore prevents local melting and enables retention in the flame of 25 the engine for a duration of over 200 ms. The thickness of the section 61 of the cap makes it possible both to minimize its weight so that it is swiftly released as indicated here above and to give it mechanical and thermal strength. To this end, the cap which is made of steel has a thickness, for example, of about 1 millimeter. The cap is made, for example, of stainless 3o steel with high mechanical characteristics.
The device according to the invention can be used under severe conditions. In particular, with regard for example to mechanical shocks of docking with and of the departure of other missiles, or with regard to vibrations in transportation, mechanical strength is obtained by maintaining 35 the cap 6 by means of serpentine coils 7. The serpentine coils are, to this end, slightly tensioned and they abut the supports 8 fixed to the container 4.
The shock-absorbing buffer 12 complements the holding action while at the same time damping the vibrations. The choice of the materials of the components of a device according to the invention furthermore enables it to withstand corrosive gases or heat shock.
A device according to the invention furthermore has great security of operation, especially through the tight sealing of certain parts, for example at the hinges as described here above, through the fact that it is rapidly released from the outlet of the nozzle as well as its great geometrical ~o deformation which moves the retained element to a relatively great distance away from the nozzle.
A device according to the invention can be delivered in the form of a kit so that it is installed especially on missiles already integrated into operational containers or batteries. More generally, it may be mounted on any missile or any pyrotechnic device already made but not provided with a retaining system. A kit comprises for example a set formed of serpentine coils 7 hinged around the cap 6 and the supports 8. These supports 8 are designed for example to be fixed to the container of a missile. The kit furthermore comprises for example a shock-absorbing buffer 12 and a bell 20 13. Since the kit is set in the plant, its installation may be done by drilling the tube of the container in particular to affix the supports 8 of the serpentine coils and then by bonding the rear hood and the sealing fixtures. An operation of this kind requires only a few minutes. It is therefore not costly.
The device according to the invention has been described by way 25 of an example for the retaining of an igniter. However, it can be applied to other elements ejected by pyrotechnic devices such as for example explosive bolts or boosters.
Claims (25)
1. A device for retaining an element ejected by a pyrotechnic device when it is fired, wherein said device comprises at least one metal cap placed behind the nozzle of the device and designed to receive the ejected element, the cap being held in position by curved rigid links, the kinetic energy of the captured element carrying along the cap and the captured element, the motion of the assembly being braked by the deformation of the rigid links.
2. A device according to claim 1, wherein the rigid links have the shape of serpentine coils.
3. A device according to claim 1, wherein the rigid links have low rupture strength.
4. A device according to claim 3, wherein the rigid links are made of soft steel.
5. A device according to claim 1, wherein the cap is held by three rigid links.
6. A device according to claim 1 wherein, with the pyrotechnic device being placed in a container, a shock-absorbing buffer is placed between the cap and the hood of the container.
7. A device according to claim 1, wherein the cap and the section of the pyrotechnic device are substantially concentric.
8. A device according to claim 1 wherein, with the pyrotechnic device being placed in a container, a rigid link is connected to the container by a support, a rigid link cooperating with the support by means of a trunnion oscillating in the support, the oscillations taking place along an axis that is substantially perpendicular to the tangent to the rigid link at the meeting point of this link with the trunnion.
9. A device according to claim 8, wherein the end of the rigid link is screwed into a tapped hole made in the trunnion, the hole being substantially perpendicular to the rotation of the trunnion.
10. A device according to claim 1, wherein a rigid link cooperates with the cap by means of a trunnion oscillating in a nut that is fixedly joined to the cap, the oscillations taking place along an axis that is substantially perpendicular to the tangent to the rigid link at the meeting point of this link with the trunnion.
11. A device according to claim 10, wherein the end of the rigid link is screwed into a tapped hole made in the trunnion, the hole being substantially perpendicular to the axis of rotation of the trunnion.
12. A device according to claim 10, wherein the cap has an aperture to let through the end of rigid link.
13. A device according to claim 10, wherein a ring is used to block the nuts which cooperate with the trunnions.
14. A device according to claim 13, wherein the ring has recessed features to enable the passage of the nuts when they are being mounted.
15. A device according to claim 1, comprising a bell fitted into the ejected element , designed to cushion the shock of arrival of this ejected element at the cap.
16. A device according to claim 15, wherein the bell is split.
17. A device according to claim 1, wherein la cap has a hollow shape generated by revolution whose aperture is opposite to the ejected element.
18. A device according to claim 1, wherein the cap has an internal funnel shape.
19. A device according to claim 18, wherein a cylindrical part goes beyond its base in the form of an ending of the funnel.
20. A device according to claim 1, wherein the section of the cap has a rounded summit facing the ejected element.
21. A device according to claim 20, wherein the sections of the cap that go from the base to the summit are rectilinear.
22. A device according to claim 1 wherein, with the pyrotechnic device being placed in a container, the rigid links are slightly tensioned and abut their supports fixed to the container.
23. A device according to claim 1, wherein the ejected element is an igniter.
24. A device according to claim 23, wherein the transmission cable for the ignition command passes through the cap.
25. A device according to claim 1, wherein the pyrotechnic device is the engine of a missile.
Applications Claiming Priority (2)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| FR9713097A FR2769975B1 (en) | 1997-10-20 | 1997-10-20 | DEVICE FOR RETAINING IN PARTICULAR THE REAR IGNITER OF A MISSILE |
| FR9713097 | 1997-10-20 |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| CA2248966A1 CA2248966A1 (en) | 1999-04-20 |
| CA2248966C true CA2248966C (en) | 2007-05-01 |
Family
ID=9512415
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CA002248966A Expired - Fee Related CA2248966C (en) | 1997-10-20 | 1998-10-19 | Retaining device, especially for the rear igniter of a missile |
Country Status (6)
| Country | Link |
|---|---|
| US (1) | US6227117B1 (en) |
| EP (1) | EP0911600B1 (en) |
| KR (1) | KR100617923B1 (en) |
| CA (1) | CA2248966C (en) |
| DE (1) | DE69812530T2 (en) |
| FR (1) | FR2769975B1 (en) |
Families Citing this family (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US7311709B2 (en) * | 2001-10-22 | 2007-12-25 | Surgrx, Inc. | Electrosurgical instrument and method of use |
| US8075558B2 (en) * | 2002-04-30 | 2011-12-13 | Surgrx, Inc. | Electrosurgical instrument and method |
| EP2887006A3 (en) * | 2013-12-21 | 2015-09-30 | JUNGHANS Microtec GmbH | Ignitor of a missile |
| CN108830023B (en) * | 2018-07-26 | 2022-07-15 | 北京理工大学 | Method for predicting ignition process of gun-launched missile booster engine |
| CN113237395B (en) * | 2021-04-26 | 2022-11-08 | 上海机电工程研究所 | Bullet fixing device based on lever mechanism |
| CN116280292B (en) * | 2023-02-20 | 2024-01-23 | 北京坤飞装备科技有限公司 | Integral steel slag diversion cone and preparation method thereof |
Family Cites Families (16)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| GB996829A (en) * | ||||
| FR1336054A (en) * | 1949-05-25 | 1963-08-30 | Monsieur Le Secretaire D Etat | Device for launching self-propelled projectiles by means of a tube closed at one end |
| US2776623A (en) * | 1949-08-06 | 1957-01-08 | Hercules Powder Co Ltd | Closure device |
| BE515185A (en) * | 1951-12-21 | |||
| FR1357624A (en) * | 1962-07-17 | 1964-04-10 | Sealing device for the nozzle of a rocket bomb | |
| DE1254509B (en) * | 1964-04-23 | 1967-11-16 | Silberhuette Pyrotechnik Veb | Hand signal |
| CH445340A (en) * | 1965-10-06 | 1967-10-15 | Oerlikon Buehrle Holding Ag | Holding device for a missile in a launch tube |
| US3674227A (en) * | 1970-03-23 | 1972-07-04 | Hughes Aircraft Co | Fragmenting cover |
| US3811360A (en) * | 1972-11-28 | 1974-05-21 | Us Army | Rocket hold back and tube closure |
| US4022343A (en) * | 1976-09-17 | 1977-05-10 | John Eric Richardson | Protective device for compressed gas cylinders |
| US4426909A (en) * | 1981-10-20 | 1984-01-24 | The Boeing Company | Noise, flash and smoke suppressor apparatus and method for rocket launcher |
| US4522103A (en) * | 1982-05-04 | 1985-06-11 | Westinghouse Electric Corp. | Trap for an umbilical plug separated from a missile |
| CH668473A5 (en) * | 1985-11-29 | 1988-12-30 | Oerlikon Buehrle Ag | DEVICE FOR SHOCK-FREE SHOOTING OF BULLETS FROM A LAUNCH TUBE. |
| FR2607914A1 (en) | 1986-12-09 | 1988-06-10 | Thomson Csf | TURRET COMPRISING A ROTATING GASKET AND A DEVICE FOR REDUCING ANGULAR SPEED |
| FR2683898B1 (en) * | 1991-11-20 | 1994-03-04 | Lacroix Tous Artifices Sa | IMPROVED SHOCK ABSORBER SYSTEM. |
| FR2685463B1 (en) * | 1991-12-24 | 1994-02-18 | Giat Industries | ANCHORAGE SYSTEM ON THE GROUND OF A PROJECTILE LAUNCHER. |
-
1997
- 1997-10-20 FR FR9713097A patent/FR2769975B1/en not_active Expired - Fee Related
-
1998
- 1998-10-13 US US09/170,279 patent/US6227117B1/en not_active Expired - Fee Related
- 1998-10-19 CA CA002248966A patent/CA2248966C/en not_active Expired - Fee Related
- 1998-10-19 KR KR1019980043658A patent/KR100617923B1/en not_active IP Right Cessation
- 1998-10-20 EP EP98402610A patent/EP0911600B1/en not_active Expired - Lifetime
- 1998-10-20 DE DE69812530T patent/DE69812530T2/en not_active Expired - Lifetime
Also Published As
| Publication number | Publication date |
|---|---|
| DE69812530T2 (en) | 2004-01-15 |
| FR2769975A1 (en) | 1999-04-23 |
| KR19990037196A (en) | 1999-05-25 |
| EP0911600B1 (en) | 2003-03-26 |
| US6227117B1 (en) | 2001-05-08 |
| EP0911600A1 (en) | 1999-04-28 |
| DE69812530D1 (en) | 2003-04-30 |
| KR100617923B1 (en) | 2006-10-24 |
| CA2248966A1 (en) | 1999-04-20 |
| FR2769975B1 (en) | 2000-01-07 |
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Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| EEER | Examination request | ||
| MKLA | Lapsed |